Results
2016-08-05: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600-2D24 (Regional Jet Series 900) airplanes, and Model CL- 600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by the discovery of a number of incorrectly calibrated angle of attack (AOA) transducers installed in the stall protection system. This AD requires replacement of affected AOA transducers. We are issuing this AD to detect and replace incorrectly calibrated AOA transducers; incorrect calibration of the transducers could result in late activation of the stick pusher.
48-22-01: 48-22-01 PRATT & WHITNEY: Applies to Martin 202, Convair 240, and Douglas DC-6 Aircraft Powered With Double Wasp Engines Equipped With Water-Alcohol Injection System. Compliance required prior to next flight. If water injection lines to carbuertor are incorporated, the water system should be blanked off. This should be accomplished by disconnecting water feed line and installing 1/2-inch pipe plug in regulator entrance. Water vent line should be disconnected at regulator and 1/4-inch pipe plug installed. Water tank should be drained and pump disconnected to preclude inadvertent water flow or pump failure from dry running. If impracticable to secure lines with tape to prevent vibration, they should be removed and stored until system reactivated. Operation of aircraft should be restricted to dry takeoff power pending correction. Water-alcohol injection systems may be reactivated provided either of the following two modifications are accomplished: 1. (a) Incorporate general control solenoid valve part 40R1009 (or equivalent approved by P&W No. 139262) in vapor vent line extending from water tank to water regulator and, (b) Incorporate Mansfield and Green Co. check valve 31-B (P&W No. 139263) in water feed line extending from water pump to water regulator. The installation of these parts should be accomplished in accordance with instructions issued by Pratt and Whitney. 2. (a) Incorporate hydraulically operated check valve Airite Products No. 1015 (or equivalent approved by Pratt and Whitney) in vapor vent line extending from water tank to water regulator and, (b) Incorporate Parker check valve No. 527-10D (or equivalent approved by Pratt and Whitney) in water feed line extending from water pump to water regulator. The installations of these parts should be accomplished in accordance with Consolidated Vultee Drawing 6121501-P.
2003-14-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus airplanes, that requires repetitive inspections for foreign objects between the slider and the girt bar attachment fittings of the emergency escape slides; a one-time inspection for correct adjustment of the slide release mechanism and the girt bar attachment fittings, which would terminate the repetitive inspections; a one-time test for correct extension of the girt bar through the sliders; and corrective action, if necessary. The actions specified by this AD are intended to prevent failure of an emergency escape slide, which could result in a delayed evacuation in an emergency and consequent injury to passengers or crew. This action is intended to address the identified unsafe condition.
2023-21-02: The FAA is superseding Airworthiness Directive (AD) 2022-18- 14, which applied to certain Airbus SAS Model A330-200 series, A330-200 Freighter series, A330-300 series, A330-800 series, and A330-900 series airplanes. AD 2022-18-14 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require the actions in AD 2022-18- 14, and also requires revising the existing maintenance or inspection program, as applicable to incorporate additional new or more restrictive airworthiness limitations; as specified in two European Union Aviation Safety Agency (EASA) ADs, which are incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
47-21-08: 47-21-08 NAVION: (Was Mandatory Note 7 of AD-782-3.) Applies to Serial Numbers NAV-4-2 Through 411. To be accomplished not later than August 1, 1947. Short circuits have been reported caused between the generator lower terminal and the fitting on the hydraulic pump inlet hose. To prevent such short circuits, install a self-threading insulator No. 145-54053 (or equivalent) on the generator lower terminal stud. (NAA Field Service Bulletin No. 18 covers this change.)
2024-23-07: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. Model EMB-545 and EMB-550 airplanes. This AD was prompted by reports of corrosion, damage, and rupture on the down lock spring assemblies of the main landing gear (MLG) and nose landing gear (NLG). This AD requires inspecting for affected MLG and NLG down lock springs and replacing affected down lock springs, and prohibits the installation of affected parts, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2001-10-14: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737, 747, 757, 767, and 777 series airplanes. This action requires repetitive inspections of any chemical oxygen generators and/or passenger, attendant, or lavatory service unit assemblies of the passenger oxygen system that have been replaced, to verify correct installation of the release pin in the generator firing mechanism of the oxygen generator; and corrective action, if necessary. This action is necessary to find and fix incorrect installation of the release pin in the generator firing mechanism, which could result in the unavailability of supplemental oxygen and possible incapacitation of passengers and cabin crew during an in-flight decompression. This action is intended to address the identified unsafe condition.
2016-08-08: We are superseding airworthiness directive (AD) 92-06-10 for SOCATA Models MS 880B, MS 885, MS 892A-150, MS 892E-150, MS 893A, MS 893E, MS 894A, MS 894E, Rallye 100S, Rallye 150ST, Rallye 150T, Rallye 235E, and Rallye 235C airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as fatigue failure of the nose landing gear wheel axle. We are issuing this AD to require actions to address the unsafe condition on these products.
2016-07-31: We are superseding Airworthiness Directive (AD) 2013-22-11 for certain The Boeing Company Model 747-400 and -400D series airplanes. AD 2013-22-11 required repetitive inspections to detect cracks in the floor panel attachment fastener holes of certain upper deck floor beam upper chords, repetitive inspections, corrective actions if necessary, and replacement of the upper deck floor beam upper chords. Since we issued AD 2013-22-11, we received a report that certain fastener holes in the upper deck floor beam upper chords may not have been inspected in accordance with AD 2013-22-11. This AD adds additional repetitive inspections for cracks for certain airplanes, and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking in certain upper chords of the upper deck floor beam. Such cracks could become large and cause the floor beams to become severed and result in rapid decompression or reduced controllability of the airplane.
2016-08-06: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300- 600 series airplanes), modified by a particular supplemental type certificate (STC). This AD was prompted by a report of chafing found on the overflow sensor harness of the surge tank, and subsequent contact between the electrical wiring and fuel tank structure. This AD requires a one-time inspection for damage of the outer tank overflow sensor harness, and repair if necessary. This AD also requires modification of the sensor harness. We are issuing this AD to prevent chafing of the harness and subsequent contact between the electrical wiring and fuel tank structure, which could result in electrical arcing and a fuel tank explosion.
73-13-09: 73-13-09 ROCKWELL INTERNATIONAL: Amdt. 39-1667. Applies to Model 690 airplanes, Serial Numbers 11001 through 11063. Compliance required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. To prevent failure of oil supply lines in the event of an engine fire, accomplish the following: Remove existing oil supply hose assembly and install tube assembly (P/N 610488-111), check valve (P/N 816T-6TT (.014)-12), hose assembly (P/N 610488-113), and attaching parts as listed in Rockwell International Service Bulletin 123, dated April 5, 1973, or equivalent parts and methods approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. This amendment becomes effective June 25, 1973.
70-10-05: 70-10-05\tBOEING: Amdt. 39-989. Applies to Model 707 and 720 series airplanes listed in Boeing Service Bulletin 2108 Revision I dated 28 December 1965. \n\n\tWithin 200 hours time in service after the effective date of this AD and after each emergency extension, inspect crank arm 65-7195 and pulley bracket 69-1087 for cracks and measure cable tension in accordance with instructions contained in the 707/720 maintenance manual. Inspections may be discontinued after modification indicated below is accomplished. \n\n\tWithin 2500 hours time in service after effective date of this AD, unless already accomplished, modify all airplanes in accordance with Boeing Service Bulletins 2108 Revision I, dated 28 December 1965 and 2108A, dated 24 May 1965, or later FAA approved revisions to these service bulletins or an equivalent modification approved by the Chief, Aircraft Engineering Division, FAA, Western Region. \n\n\tThis amendment becomes effective May 16, 1970.
2024-23-06: The FAA is adopting a new airworthiness directive (AD) for certain MD Helicopters, LLC (MDHI), Model 369, 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, 369HS, 500N, and 600N helicopters. This AD was prompted by a report of a seized and damaged roller bearing in the pilot interconnecting cyclic torque tube (torque tube) assembly. This AD requires repetitively inspecting the torque tube assembly and roller bearings, and depending on the results, replacing parts, or accomplishing additional inspections. The FAA is issuing this AD to address the unsafe condition on these products.
2016-08-04: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-223F and -243F airplanes. This AD was prompted by a report of missing fasteners in certain locations of the fuselage during production. This AD would require inspecting for missing, damaged, or incorrectly installed fasteners; and corrective actions if necessary. We are issuing this AD to detect and correct cracking of the fuselage due to missing, damaged, or incorrectly installed fasteners, which could result in reduced structural integrity of the fuselage.
2016-07-28: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes, and Model MD-88 airplanes. This AD requires repetitive eddy current high frequency (ETHF) inspections for any cracking in the left and right side center wing lower skin, and corrective actions if necessary. This AD was prompted by reports of cracking at certain stringers, associated end fittings, and skins in the center wing fuel tank where the stringers meet the end fittings. We are issuing this AD to detect and correct cracking in the center wing lower skin. Such cracking could cause structural failure of the wings.
47-50-09: 47-50-09 FAIRCHILD: Applies to 24R and 24W Series Aircraft. Inspection required each 100 hours of operation. Inspect the landing gear fittings near the lower longeron attachment and also the fuselage fittings for cracks. Cracks in the strut not exceeding 1/8 inch in length may be repaired by electric arc welding. Cracks in excess of 1/8 inch in length should be stop drilled and oxyacetylene welded, and the landing gear strut should be re-heat-treated to 180,000 pounds per square inch. (Fairchild Service Bulletin No. 41-8 dated June 23, 1941, covers this subject.)
71-26-03: 71-26-03 SIKORSKY AIRCRAFT: Amdt. 39-1363. Applies to Sikorsky S-62A and S- 55 type Helicopters certified in all categories. Compliance required as follows: To preclude the failure of the S-62A and S-55 Servo Support Bracket P/N 1440-2415. 1. Unless already accomplished within the last 95 hours in service, inspect the servo support bracket within the next 25 hours in service after the effective date of this AD, in accordance with Part I subparagraph A and B of Accomplishment Instructions of Sikorsky Service Bulletins 55B40-6 or 62B40-8 as applicable dated October 1, 1971 or later FAA- approved revision or an alternate method approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 2. Inspect the bracket within 120 hours in service after the inspection in paragraph 1 of this airworthiness directive and every 120 hours thereafter in accordance with Part I subparagraph B of Accomplishment Instructions of Sikorsky Service Bulletins 55B40-6 or 62B40-8 as applicable dated October 1, 1971 or later approved revision or an alternate method approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 3. Conduct fluorescent magnetic particle inspection in accordance with Part II Accomplishment Instructions of SIK S/B 55B40-6 or 62B40-8 as applicable at gear box overhaul or 1250 hours, whichever comes first; or an alternate method approved by Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective December 30, 1971.
2016-08-07: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-22B and RB211-524 turbofan engines with low- pressure turbine (LPT) support roller bearing, part number (P/N) LK30313 or P/N UL29651, installed. This AD requires removal of certain LPT support roller bearings installed in RR RB211-22B and RB211-524 engines. This AD was prompted by a report of a breach of the turbine casing and release of engine debris through a hole in the engine nacelle. We are issuing this AD to prevent failure of the LPT support roller bearing, loss of radial position following LPT blade failure, uncontained part release, damage to the engine, and damage to the airplane.
2016-07-18: We are adopting a new airworthiness directive (AD) for certain Airbus Defense and Space S.A. Model CN-235-200 and CN-235-300 airplanes. This AD was prompted by reports of false engine fire warning events, which consequently led to engine in-flight shutdowns. This AD requires modification of the location and routing of the engine fire detection system. We are issuing this AD to prevent unnecessary engine in-flight shutdown, which could result in reduced controllability of the airplane.
67-25-04: 67-25-04 FAIRCHILD: Amdt. No. 39-472, Part 39, Federal Register May 30, 1967. Applies to Type F-27 Airplanes, Serial Numbers 108 through 123, inclusive, and FH-227 Airplanes, Serial Numbers 503, 506, through 518, 520 through 535, and 538. Due to numerous elongated and double-drilled rivet holes found in the fuselage skin, accomplish the following within the next 150 hours' time in service after the effective date of this AD unless already accomplished. (a) For F-27 Airplanes, comply with the Accomplishment Instructions of Fairchild-Hiller Service Bulletin No. 53-49 (F-27), dated April 14, 1967 and FH-227 Airplanes, comply with Accomplishment Instructions of Fairchild Hiller Service Bulletin No. 53-7 (FH-227), dated April 14, 1967, or later FAA-approved revisions, or FAA-approved equivalent modification. (b) Equivalent inspections may be approved by an FAA maintenance inspector. Equivalent parts, Service Bulletin revisions, and modifications, must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (c) Upon request with substantiating data submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment effective September 8, 1967.
50-31-01: 50-31-01 CESSNA: Applies to All Models 120 and 140 Aircraft, Serial Numbers 8001 to 15035, Inclusive, on Which the 0.051 Reinforcing Channel or 0.040 Reinforcing Angles Have Not Been Installed. Compliance required as soon as possible and not later than August 1, 1950, except as indicated below. Because two fin spar fatigue failures have occurred in flight, indicating inadequate inspection due to the difficulty of such inspection, the fin must be removed for inspection. Inspection can then be best accomplished by removing five rivets in the fin bottom rib skin attachment and all attaching rivets through the spar and doubler flanges to permit raising the adjacent skin. The front face of the spar and the spar reinforcing channel should then be carefully inspected for flange buckles or cracks with at least an 8-power magnifying glass in the bend radii and in the adjacent flange rivet or clearance holes in the region of the bottom rib attachment. Modify in accordance with item 1 or 2 herein: 1. If failure exists, the spar must be replaced with a spar incorporating an 0.051 24ST alclad fin spar reinforcing channel, Cessna P/N 0431129, or equivalent. 2. If no failure exists, reinforcing angles, Cessna P/N 0431145 and 1431145-1 or equivalent, must be installed. (Cessna Service Letter No. 62 dated April 10, 1950, covers this same subject.) Some of the first airplanes were manufactured using spot welded instead of riveted construction. The following applies to these aircraft and should be accomplished not later than September 1, 1950: Drill out center of spots with No. 30 drill. Carefully pry skin loose from spar and root rib using a thin lever. Inspect and accomplish 1 or 2 above replacing all drilled spot welds with 1/8- inch rivets as required. In case that sheet or underlying structure is left with a damaged hole which cannot be properly filled with a 1/8-inch rivet, replace with 5/32-inch rivet or add an additional 1/8-inch rivet on each side of damaged hole. This supersedes AD 50-17-01.
2024-22-06: The FAA is superseding Airworthiness Directive (AD) 2023-21-06 for certain Embraer S.A. (Embraer) Model EMB-505 airplanes. AD 2023-21- 06 required installing structural reinforcements on certain monuments and replacing certain floor support rivets. Since the FAA issued AD 2023-21-06, the FAA determined that certain airplanes need to be re- assigned to a different group and certain re-identified floor support part numbers need to be corrected. This AD requires installing structural reinforcements on monuments and replacing fasteners on the floor support, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2016-07-20: We are superseding Airworthiness Directive (AD) 95-18-08 for all Airbus Model A300-600 series airplanes. AD 95-18-08 required repetitive inspections to detect cracks in the bottom skin of the wing in the area of the cut-out for the pylon rear attachment fitting, and repair if necessary. This new AD, for certain [[Page 21256]] airplanes, reduces the compliance times for the inspections. This AD was prompted by a report that updated fatigue and damage tolerance analyses and a fleet survey found that certain inspection thresholds and intervals must be reduced to allow more timely findings of cracking. We are issuing this AD to detect and correct fatigue-related cracking in the bottom skin of the wing in the area of the cut-out for the pylon rear attachment fitting, which could result in reduced structural integrity of the wing.
58-13-03: 58-13-03 LOCKHEED: Applies to All Model 1649A Aircraft. Compliance required as indicated. Model 1649A aircraft have been found to have possible hazardous wing bending oscillation, dynamically induced by aileron oscillation, under certain combinations of boost package tolerances and autopilot modulating piston follow-up failure. In order to correct this condition, the following must be accomplished: Modify the aileron control valve by installing a new modulating piston stop to meet limits of aileron deflection rates of 7.5 degrees per second minimum and 11 degrees per second maximum. The valve is then to be reidentified as 668152-11 and to be painted yellow to denote noninterchangeability with elevator and rudder valves. Details of the necessary modifications are given in Lockheed communication FS/225805-W, dated June 13, 1958. This modification is to be accomplished as soon as maintenance schedules will permit but not later than January 1, 1959. Until the modification is accomplished, the airplane must be flown in autopilot operation at speeds not to exceed 215 KIAS. This supersedes AD 58-11-04.
75-09-17: 75-09-17 HUGHES: Amendment 39-2191. Applies to Model 369H Series Helicopters certificated in all categories, configured with "four-on-the-floor" passenger interior in accordance with Drawing 369H90035. Compliance required as indicated unless already accomplished. To provide adequate protection for the occupants of the aft facing seats, accomplish the following: (a) Within the next 25 hours' time in service after the effective date of this AD, install two conspicuous placards worded, "DO NOT OCCUPY FOR TAKEOFF AND LANDING". The placards must be located on the aft face of the forward divider, facing aft, centered on divider, above each seat cushion. (b) Placards may be removed upon installation of a modification approved by the Chief, Aircraft Engineering Division, FAA Western Region, which provides the required occupant head and back support. This amendment becomes effective May 2, 1975.